View from above orbital plane
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View from above satellite
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Ground track
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The orbit is defined by the following mean orbital elements,
1 09023U 26070.16362628 +.00000000 +00000-0 +98440-4 0 00005
2 09023 74.0442 327.1396 0015949 63.5066 296.7723 14.41185940 05
| Epoch (UTC): | 11 March 2026 03:55:37 |
| Eccentricity: | 0.0015949 |
| inclination: | 74.0442° |
| perigee height: | 743 km |
| apogee height: | 766 km |
| right ascension of ascending node: | 327.1396° |
| argument of perigee: | 63.5066° |
| revolutions per day: | 14.41185940 |
| mean anomaly at epoch: | 296.7723° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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